Molding tool and method for manufacturing a fiber reinforced plastic aerodynamic aircraft component
US-9144949-B2 · Sep 29, 2015 · US
US11097450B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11097450-B2 |
| Application number | US-201815962888-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 25, 2018 |
| Priority date | Oct 29, 2015 |
| Publication date | Aug 24, 2021 |
| Grant date | Aug 24, 2021 |
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A core system for the production of a fiber composite component includes at least two core elements which are coupled to one another and are displaceable relative to one another. At least one core element has a surface which is oblique to a displacement direction. A method for producing the fiber composite component uses the core system.
Opening claim text (preview).
What is claimed is: 1. A core system for the production of a fiber composite component, comprising: a plurality of core elements which are coupled to one another and are displaceable relative to one another, wherein a first core element of the plurality of core elements is a main core element which has a substantially rectangular cross-section, wherein a second core element of the plurality of core elements has an internal face that is oblique to a displacement direction and an external face that is not oblique to the displacement direction and that is a part of a rectangular shell face of the core system, wherein the second core element has a substantially decreasing cross-section such that a first cross-section at a first longitudinal end of the second core element is smaller than a second cross-section at a second longitudinal end of the second core element and is wedge-shaped, and wherein the core system has a rectangular cross-section. 2. The core system as claimed in claim 1 , wherein the plurality of core elements each have at least one external face which is part of the rectangular shell face of the core system and at least one contact face via which the plurality of core elements bear on one another. 3. The core system as claimed in claim 2 , wherein the at least one contact face and the at least one external face of at least one core element of the plurality of core elements run in a mutually oblique manner. 4. The core system as claimed in claim 1 , wherein the plurality of core elements are configured from a hard material. 5. The core system as claimed in claim 4 , wherein the hard material is a metal. 6. A use of the core system as claimed in claim 1 as a core in a production of a fiber composite component. 7. A method for producing a fiber composite component, comprising the acts of: a) displacing a first core element of a plurality of core elements of a core system in relation to a second core element of the plurality of core elements along a displacement direction wherein the second core element is a main core element which has a substantially rectangular cross-section, wherein the first core element has an internal face that is oblique to the displacement direction and an external face that is not oblique to the displacement direction and that is a part of a rectangular shell face of the core system, has a substantially decreasing cross-section such that a first cross-section at a first longitudinal end of the first core element is smaller than a second cross-section at a second longitudinal end of the first core element, and is wedge-shaped and wherein the core system has a rectangular cross-section; b) circumferentially braiding the core system with fibers; c) incorporating a matrix-forming material in the braided fibers; d) curing the matrix-forming material to produce the fiber composite component; and e) removing the core system from the produced fiber composite component. 8. The method as claimed in claim 7 , wherein the plurality of core elements prior to step e) are displaced in relation to one another. 9. The method as claimed in claim 7 , wherein the plurality of core elements during step c) and/or step d) are displaced in relation to one another. 10. The method as claimed in claim 8 , wherein the plurality of core elements during step c) and/or step d) are displaced in relation to one another. 11. The method as claimed in claim 7 , wherein at least one core element of the plurality of core elements is heated. 12. The method as claimed in claim 8 , wherein at least one core element of the plurality of core elements is heated. 13. The method as claimed in claim 9 , wherein at least one core element of the plurality of core elements is heated.
for stripping articles from a mould core, e.g. using stripper plates · CPC title
on a rotating mould, former or core · CPC title
having a non-circular cross-section · CPC title
and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM] {, e.g. by vacuum} · CPC title
collapsible, e.g. elastic or inflatable; with removable parts, e.g. for regular shaped, straight tubular articles (B29C53/825 takes precedence) · CPC title
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